By Rolf Radespiel, Reinhard Niehuis, Norbert Kroll, Kathrin Behrends
The publication reviews on complicated ideas to the matter of simulating wing and nacelle stall, as offered and mentioned via the world over well-known researchers on the remaining Symposium of the DFG study Unit FOR 1066. trustworthy simulations of circulate separation on airfoils, wings and powered engine nacelles at excessive Reynolds numbers characterize nice demanding situations in defining compatible mathematical versions, computing numerically exact recommendations and supplying finished experimental facts for the validation of numerical simulations. extra difficulties come up from the necessity to ponder airframe-engine interactions and inhomogeneous onset circulate stipulations, as genuine plane function in atmospheric environments with often-large distortions. The findings of basic and utilized examine into those and different similar concerns are stated intimately during this e-book, which objectives all readers, lecturers and execs alike, drawn to the improvement of complicated computational fluid dynamics modeling for the simulation of advanced airplane flows with movement separation.
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Extra info for Advances in Simulation of Wing and Nacelle Stall Results
ST forcing domain t' RANS LES = − ∆ (6) t ST forcing domain RANS LES r' r' r Δr Fig. 1 Sketch of the trajectory of a single vortex structure within the ST forcing domain. Left: Position of the vortex at the time t', right: Position of the vortex at the time t= t'+∆r/Uconv The implementation of this forced convection based on Taylor’s frozen hypothesis considerably speeds up the transition to the fully developed solution in the LES domain. Its assessment through a ZPG flat plate in terms of mean skin friction coefficient distribution has shown a significant reduction in the distance required to reach the fully developed solution .
Aref is defined as a proper average of the tensor A distribution at the RANS/LES interface so as to keep the spatial independence of dn which is essential for the spatial correlation features of the generator. With the second modification, the energy spectrum was conditioned to avoid the abrupt reduction in the most energetic length scale of the turbulence at the edge of the boundary layer. This abrupt reduction had been previously shown to produce a significant increase of the generated velocity field divergence at the edge of the boundary layer .
The implementation was assessed with wall-resolved embedded LES approaches in a zero-pressure-gradient (ZPG) flat plate, for the HGR-01 airfoil and for a flow-through nacelle. The results show important improvements with respect to computations performed without forcing of synthetic turbulence, reducing considerably the grey area and providing significant enhancements of the overall solution. However, the overall quality of this solution does also depend on the solver numerical settings and the grid resolution.